Examination of the theoretical possibility of creating a vernier electrorocket engine

The report examines the possibility of creating a vernier electric rocket engine. All engines feature hightemperature combustion products from the engine nozzle that will be vented to the outside. The proposed motor will operate as follows: the working fluid (liquid) is supply through the porous insert into the combustion chamber via a gear pump. In fluid flow through porous insert, the liquid takes the temperature of the insert and may exceed it under certain conditions. These conditions are low porosity inserts (less than 0.05). The process will proceed in two stages. The first stage liquid is converted to steam, which is then heated to a temperature of the porous insert, and may exceed it as a porous insert can be used the porous materials made of a metal having a melting point from the melting point to the melting point of copper tungsten. In the second stage, the energy obtained in the first step is liberate in the nozzle apparatus for producing thrust. The energy input to the transformation from liquid to vapor and overheating by setting HDTV. Efficiency of these plants is 95%. Thus, the combustion chamber working fluid is at a temperature necessary to achieve the desired parameters of the rocket engine.